Wingless aircraft

ABSTRACT

A wingless aircraft that has a generally truncated cone fuselage that has a cockpit in the upper thereof in which the pilot sits, and a transparent rigid dome mounted on the upper portion of the fuselage that extends over the pilot. A number of equally spaced, elongate, jet engine assemblies are pivotally and adjustably supported within the fuselage, with each engine in communication with an air inlet defined in the fuselage. Each jet engine assembly includes a combustion chamber that has an elongate tubular nozzle extending downwardly therefrom, in which exhaust openings are defined through which the hot gaseous products of combustion discharge. The exhaust openings are elongate and substantially angularly disposed relative to the vertical, and as a result the exhaust gases not only rotate the nozzle but exert a reactive force sufficient to lift the fuselage to an airborne position. Rotation of the nozzles results in concurrent rotation of fans that compress air entering the intakes prior to it being discharged to the combustion chambers to mix with atomized fuel and burned to produce the gases of combustion. Guidance of the aircraft is achieved by angular movement of the rotating nozzles relative to the fuselage.

DESCRIPTION OF THE PRIOR ART

In the past, numerous attempts have been made to devise a winglessaircraft, but such attempts have met with but limited success.

A major object of the present invention is to provide a winglessaircraft that has a cone shaped overall appearance, is powered by anumber of internally positioned, pivotally and adjustably supportedelongate jet engines that each has a rotatable downwardly extendingnozzle, with exhaust from combustion of fuel not only causing rotationof the nozzles to drive fans to compress air prior to it entering thecombustion chamber, but developing a thrust to maintain the aircraftairborne, and guidance of the aircraft being achieved by varying theangle of the nozzles relative the fuselage.

Another object of the invention is to overcome operational disadvantagesof prior art wingless aircraft by providing one that is simple and easyto fly, has a simple mechanical structure, requires a minimum ofmaintenance attention, and when not in use may be stored in a relativelysmall confined space.

These and other objects of the invention will become apparent from thefollowing description of a preferred form thereof.

SUMMARY OF THE INVENTION

The wingless, jet engine, propelled aircraft of the present inventionhas a generally conical shaped fuselage, which in the upper portion isdefined by a upwardly convex transparent rigid shield that protects thepilot who is disposed directly there below, when in the aircraft. Thefuselage at substantially mid point of the fuselage has a number ofscreened air intake openings defined therein, with each of the openingsbeing in communication with a jet engine assembly that is pivotallysupported within the fuselage, and the nozzle of each jet engine beingdisposed downwardly for gases of combustion that discharge from thenozzle to be directed downwardly to impart an upward force to theaircraft. Each of the jet engines includes first and second propellersdisposed within a shroud that extends inwardly from one of the airintakes to communicate with a combustion chamber that has a number offuel atomizing nozzles that are connected by conduits to one of a numberof fuel tanks situated within the fuselage. The fuel-air mixture in thecombustion chamber is initially ignited by spark plug of the like, withthe mixture after initial ignition continuing to burn. Products ofcombustion resulting in the burning of the fuel are directed downwardlythrough a converging section to a tubular nozzle that is rotatablysupported therefrom.

The combustion chamber and nozzle that is rotatably supported therefromin a downwardly depending position are situated within the confines of atubular housing, which housing on the upper end has a ring shaped memberextending outwardly therefrom that has a circular transverse crosssection. The circular member is pivotally supported by engagement by arigid ring that has a transverse interior surface of circular transversecross section and of substantially the same radius of curveture as theexterior surface of the convex ring secured to the tubular housing. Thecircular ring is supported by a spider that extends to a depth that isin communication with one of the air intakes, and extends downwardly toan opening formed in the bottom of the fuselage.

As the fuel-air mixture is burned within the combustion chamber, hotgases of combustion are generated therein and discharged downwardlythrough the nozzle to be emitted through a number of elongate dischargeopenings that are angularly disposed at a substantial angle relative tothe bottom of the vehicle. The lower end of each nozzle is sealed by anupwardly extending member that has a shaft continuing upwardly therefromto terminate in at least one set of propellers situated adjacent the airintake. As fuel is burned in the combustion chamber hot gases ofcombustion discharge downwardly through the openings in the nozzle torotate the same, as well as the shaft and propeller and also to continueflowing downwardly through the tubular shell as a stream of gases atsubstantial velocity which imparts an upward thrust to the engine andthe fuselage secured thereto. Rotation of the shaft and propellerpreviously described results in air flowing into the air intake beingcompressed to a substantial degree prior to entering the combustionchamber and burning in combination with the fuel that is dischargedthere into.

The invention includes a number of jet engine assemblies as abovedescribed, each of which is equally spaced from the other within thefuselage, and each of the jet engine assemblies being pivotally movableto direct the downward flow of gases of combustion therefrom, inguidance of the aircraft being achieved by varying the angulation of thejet engine containing shells relative to one another. As the angulationof the downwardly extending nozzles are varied, the direction of gasesof combustion are flowing therefrom is changed, and as a result thedirection of movement of the aircraft through the air may be controlledby the pilot varying the angulation of the jet engines in the tubularshells that enclose the rotating nozzles. Initiation of the operation ofeach of the jet engines above described is by an electric motor or otherprime mover driving a propeller situated in one of the air intakes, todirect a downward flow of air through the combustion chamber andcooperate with fuel discharged thereinto to provide a stream of gases ofcombustion that flow downwardly through the rotating nozzle and shell.After the nozzle of each engine is rotating, the shaft associated withthat nozzle is driving a first set of propellers, and the motor set ofpropellers is disconnected. Driving the first set of propellers resultsin an air stream being directed downwardly through the combustionchamber to mix with atomized fuel ejected thereinto, and the air-fuelmixture burning to provide the downwardly flowing stream of gases ofcombustion that result in rotation of the nozzle associated with thatparticular engine, and also due to the stream of gases dischargingthrough one of the tubular shells effecting an upward lift on thefuselage to cause it to rise. After the fuselage is airborne, guidanceof the fuselage is achieved by varying the angulation of the nozzlesrelative to the fuselage and to one another.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a side elevational view of the wingless jet propelledaircraft;

FIG. 2 is a top plan view of the aircraft shown in FIG. 1;

FIG. 3 is a fragmentary vertical transverse cross sectional view takenon the line 3--3 of FIG. 2;

FIG. 4 is the same view as shown in FIG. 3 but with the jet engineassembly having been tilted to an angular position relative to thevehicle for guiding purposes;

FIG. 5 is a bottom plan view of the aircraft;

FIG. 6 is a bottom plan view of one of the jet engine assemblies andillustrating in phantom line the position to which the lower end of thenozzle may be manipulated by the pilot of the invention;

FIG. 7 is a vertical, enlarged, cross sectional view of one of the jetengine assemblies and movable support therefor taken on the line 7--7 ofFIG. 5;

FIG. 8 is a transverse cross sectional view of the invention taken onthe line 8--8, and illustrating two sets of propellers that are utilizedin compressing air prior to the same being discharged into thecombustion chamber of one of the engines;

FIG. 9 is a transverse cross sectional view of one of the engineassemblies, taken on the line 9--9 of FIG. 7;

FIG. 10 is a fragmentary enlarged side elevational view of one of theelongate upwardly and angularly disposed gaseous products of combustionopenings formed in one of the nozzles and taken on the line 10--10 ofFIG. 9.

DESCRIPTION OF THE PREFERRED EMBODIMENT

The wingless jet engine propelled aircraft A as may best be seen in FIG.1 includes a generally frustoconical shaped fuselage B, that on theupper ends supports a transparent protective rigid dome C, and with acockpit D situated therebelow in which the pilot (not shown) is seated.The aircraft A is illustrated as including four fuel tanks E as may beseen in FIG. 2 that are situated within the confines of the fuselage andequally spaced from one another. The fuselage B has four intakes Fformed therein, with four jet engine assemblies G of elongate shapebeing disposed within the fuselage B and in communication with the airintakes F. Each of the jet engine assemblies G which is of elongateshape as may be seen in FIG. 3 is situated in a downwardly extendingshroud H that has the upper end secured to the sheet material 10defining the fuselage B. The shell 10 develops on the lower end into aconvex portion 10a that merges into a flat bottom 12, as shown inFIG. 1. Each shroud as may best be seen in FIG. 3 includes a cylindricalmember 14 secured to the shell 10, and extending downwardly therefrom,which cylindrical member develops into a converging section 16 ofcircular transverse cross section.

Each of the converging sections 16 on the lower end develops into a ring18, which ring on the lower end develops into a diverging section 20 ofcircular transverse cross section that merges into the bottom 12.

Each shroud H defines an interior confines space J that is open at thebottom as shown in FIG. 3. In FIG. 3 it will be seen that each shroud Hincludes a cylindrical member 14 secured to the shell 10, with thecylindrical member 14 on the lower end merging into a converging section16. Each section 16 on the lower end develops into a ring 18, from whicha diverging section 20 extend downwardly to merge into the bottom 12.

Each of the jet engines G as may best be seen in FIG. 7 includes an airintake portion 22 that is partially defined by a first cylindrical shell24, that on the lower end thereof develops into a converging section 26.The section 26 on the lower end merges into the upper end of a secondcylindrical shell 28. The shell 28 on the lower end develops into adownwardly and outwardly converging section 30 that has the outer endthereof in communication and secured to the upper outer portion of acylindrical combustion chamber 32. The combustion chamber 32 on thelower end develops to an inwardly converging section 34 that has a lowertapered opening 34a defines therein.

A tubular shell 36 is provided for each of the jet engines G as may beseen in FIG. 7, with the shell being secured by conventional means tothe exterior surface of the combustion chamber 32.

A first ring shaped member 38 is secured to the upper exterior portionof the shell 36, with the ring 38 having an exterior surface of 40 ofcircular cross section. A second ring 42 of substantially less widththan that of the first ring 38 is provided, which second ring has aninterior convex surface 44 that is of circular shape and slidablyengages the surface 40 to permit the first ring 38 to pivot relative tothe second ring 42. The second ring 42 is supported by a spider 46 fromthe ring 18 as may be seen in FIG. 3.

In FIG. 7 it will be seen that a number of fuel injecting nozzles 48 areprovided that discharge fuel into the interior of the combustion chamber32, which fuel is delivered to the nozzles from conduits 50 that extendto one of the tanks E in which the fuel is pressurized. The opening 34arotatably engages the flared upper end 52 of a cylindrical nozzle 54that extends downwardly in the tubular shell 36 and is concentricallydisposed therein. The cylindrical nozzle 54 has a number oflongitudinally and circumferentially spaced discharge openings 56 formedtherein as may be seen in FIG. 10, each of the openings being oftriangular configuration and extending upwardly relative to the bottom12 at a substantial angle. A collar 58 is secured to the exteriorsurface of the tubular nozzle 54 adjacent the upper outwardly flared end52 thereof. The collar 58 is rotatably supported in a ring shapedrecessed bearing 60, which bearing is supported in a fixed positionrelative to the tubular shell 56 by a first spider 62. Each cylindricalnozzle 54 on the lower end thereof has a second collar 64 securedthereto that is rotatably supported in a second bearing 66. The bearing66 is maintained at a fixed position relative to the tubular shell 36 bya second spider 68.

Each tubular nozzle 54 is illustrated as in FIG. 7 as including anelongate plug 70 of generally triangular vertical transverse crosssection, which plug has a shaft 72 extending upwardly therefrom into theair intake portion 22. The shaft 72 on the upper end thereof supports afirst and second propeller 74 and 76 that are preferably verticallyspaced from one another. The upper end of the shaft 72 has a recess 78formed therein that is rotatably engaged by a second shaft 80. Therecess 78 is engaged by a shaft 80 that supports third and fourthpropellers 82 and 84. The shaft 80 and the propellers 82 and 84 mayinitially be driven by an electric motor 86 or like prime mover toinitiate operation of the jet engine assembly G with which it isassociated. The combustion chamber 32 has a fuel-air mixture ignitingdevice 86 mounted thereon, which is used only in the starting of the jetengine assembly.

In operation, each of the jet engines G is initially actuated by causingthe electric motor 86 to rotate the third and fourth propellers 82 and84 to direct a current of air downwardly through the combustion chamber32. Concurrently, fuel is delivered through the conduits 50 to theatomizing nozzles 48, where a fuel-air mixture is formed in thecombustion chamber 32. The fuel igniting device 86 which may be a sparkplug or the like causes the fuel-air mixture to ignite, with hot gasesof combustion being directed downwardly through the nozzle 54 todischarge tangentially through the openings 56, and in so doing causingrotation of the nozzle 54 together with the shaft 72. Rotation of theshaft 72 results in rotation of the first and second propellers 74 and76 to draw air into the intake 22 and compress the same as the air isdirected downwardly into the combustion chamber 32. The air flowingdownwardly is mixed with the fuel to form a combustable mixture, whichburns and with the hot gases of combustion flowing downwardly throughthe nozzle 54 to cause the same to rotate as it discharges through theopenings 56. The hot gases of combustion after discharging through theopenings 56 flow downwardly through the shell 36 in the direction of thearrows shown in FIG. 7 in the lower portion thereof, and thesedischarging gases imparting an upward force to the aircraft A to causethe same to lift from the ground surface M. After each engine is inoperation as above described, the motor 86 is no longer supplied withcurrent through the conductors 87, and accordingly no longer drives thethird and fourth propellers 82 and 84.

Each of the jet engine assemblies G may be pivotally moved by pairs ofcables 100 that are secured thereto above combustion chamber 32, withthe cables extending through openings 102 in the shroud H associatedwith that engine to the cockpit where they are secured to manuallymovable members or other conventional control devices (not shown) thatmay be manipulated by the pilot. Each jet engine has a cone shapeddeflector 106 secured to the nozzle 54 thereof as shown in FIG. 7 todirect the jet of hot gases of combustion downwardly in the tubularshell 36 associated therewith.

The construction and operation of the wingless aircraft A has beendescribed previously in detail and need not be repeated.

What is claimed is:
 1. A wingless aircraft that includes:a. a truncatedcone shaped fuselage assembly that includes a bottom that has aplurality of circumferentially spaced openings therein, a side wall thattapers upwardly and inwardly from said bottom; a convex transparent domeremovably secured to the upper portion of said side wall; a cockpit fora pilot situated in said fuselage below said dome; a plurality ofcircumferentially spaced fuel tanks disposed within said fuselage, aplurality of air intake openings in said side wall, and a plurality oftubular shrouds disposed within said fuselage each of said shroudscommunicating with one of said air intake openings and one of saidopenings in said bottom, each of said shrouds defining a compartmentisolated from the balance thereof; b. a plurality of elongate jet engineassemblies, each of said jet engine assemblies including an air intake,a combustion chamber and a nozzle for hot gases of combustion thatextend from said combustion chamber in a direction opposite from that ofsaid air intake, each of said nozzles being an elongate tubular memberhaving a lower end, and a plurality of elongate upwardly extendingopenings in each of said nozzles through which pressurized gases ofcombustion from the burning of said air and fuel discharge tangentially;c. first means for pivotally supporting each of said jet engineassemblies in one of said compartments, with said nozzle and said jetengine extending downwardly; d. second means for supplying atomized fuelfrom said fuel tanks to said combustion chambers; e. third means forcompressing air from said air intake openings prior to it discharginginto said air intakes of said jet engines; f. fourth means forinitiating burning of said atomized fuel and compressed air in saidcombustion chambers to develop a plurality of thrusts through saidnozzles that will lift said aircraft from the ground; g. fifth means forrotatably supporting said nozzles from said combustion chambers; h. aplurality of cylindrical shells disposed within said shrouds that extendaround said nozzles and are secured to said engine assemblies; i. aplurality of deflectors disposed in said cylindrical shells above saidopenings, said deflectors serving to direct hot gases of combustiondischarging from said openings in said nozzles downwardly to exert anupward thrust on said aircraft to dispose the latter in an airborneposition, said gases of combustion as they discharge tangentiallythrough said openings in said nozzles causing the latter to rotate; j. aplurality of plugs that close the lower ends of said nozzles and arerigidly secured thereto; k. a plurality of shafts that extend upwardlyfrom said plugs through said combustion chambers to positions adjacentsaid air intakes; l. sixth means rotated by said shafts for compressingair entering said air intakes from said air intake openings prior tosaid air entering said combustion chambers; and m. seventh meansmanually actuatable from said cockpit for pivoting said jet engineassemblies after said aircraft is airborne to so dispose the directionof thrust of said gases of combustion from said nozzles as to guide saidaircraft when the latter is airborne.
 2. An aircraft as defined in claim1, in which said sixth means are propellers mounted in said air intakesof said jet engine assemblies and driven by said rotation of said plugsand nozzles.
 3. An aircraft as defined in claim 2, which in additionincludes:eighth means for discharging current of air downwardly throughsaid combustion chambers to initially start combustion of fuel and airtherein.
 4. An aircraft as defined in claim 3, in which said eighthmeans includes:a plurality of prime movers mounted in intermediatepositions between said air intake openings and said air intakes; and aplurality of second propellers situated above said first propellers thatare initially driven by said prime movers.
 5. An aircraft as defined inclaim 4, in which said prime movers are electric motors.